US5283985A - Extreme energy method for impacting abrasive particles against a surface to be treated - Google Patents

Extreme energy method for impacting abrasive particles against a surface to be treated Download PDF

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US5283985A
US5283985A US08/045,229 US4522993A US5283985A US 5283985 A US5283985 A US 5283985A US 4522993 A US4522993 A US 4522993A US 5283985 A US5283985 A US 5283985A
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flow
supersonic
nozzle
elongated duct
jet stream
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US08/045,229
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James A. Browning
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
    • B24C1/086—Descaling; Removing coating films
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C5/00—Devices or accessories for generating abrasive blasts
    • B24C5/02—Blast guns, e.g. for generating high velocity abrasive fluid jets for cutting materials
    • B24C5/04—Nozzles therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C5/00—Devices or accessories for generating abrasive blasts
    • B24C5/08—Devices for generating abrasive blasts non-mechanically, e.g. of metallic abrasives by means of a magnetic field or by detonating cords
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C7/00—Equipment for feeding abrasive material; Controlling the flowability, constitution, or other physical characteristics of abrasive blasts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/03005—Burners with an internal combustion chamber, e.g. for obtaining an increased heat release, a high speed jet flame or being used for starting the combustion

Definitions

  • This invention relates to sand blasting surfaces by impacting abrasive particles against such surface, and more particularly to the use of an internal burner in which an oxy-fuel mixture is combusted at very high pressure, with the abrasive particles for sandblasting introduced to the expanded gas products of combustion and accelerating such particle in an extended nozzle length downstream of the particle introduction point into expanded gases at near atmospheric pressure.
  • the present invention is directed to a method of impacting abrasive particles against a surface to be treated, using an internal burner by introducing the abrasive particles into the supersonic jet stream after expansion of the product of combustion gases from the internal burner to nearly atmospheric pressure from very high pressures of the combustion chamber, and by causing the abrasive particles in their supersonic jet stream carrier gas to travel through an extended nozzle length, which nozzle length is long enough to accelerate the particles to much greater impact velocity than heretofore possible using either conventional compressed air sandblasting equipment or the air-fuel internal burner devices of my earlier patents, discussed above.
  • the single figure is a cross-sectional view of an internal burner employing the method forming a preferred embodiment of the invention.
  • FIG. 1 is a cross-sectional view of an internal burner suitable for practicing the method of this invention.
  • the internal burner indicated generally at 10' is comprised of a unitary metal, main body 10 of elongated cylindrical form which includes an axially positioned combustion chamber 11 of elongated cylindrical form, which is open at an upstream end 11a, to a small diameter axial bore or oxygen supply duct 12 receiving a source of oxygen under pressure as indicated by the labeled arrow.
  • a fuel and oxygen mixture is effected by feeding fuel as indicated by the arrow labeled FUEL through a radial passage 13, which is at right angle to axial passage 12 and which intersects the same.
  • the fuel and air mixture enters the combustion chamber and is combusted by a spark ignition device (not shown) or other conventional means.
  • the downstream end 11b of the combustion chamber opens directly to a restricting nozzle throat 14 leading to a supersonic expansion nozzle section 15 of relatively short length.
  • the internal burner 10' terminates in an integral, extended nozzle length 16 which is two, three or more times the combined length of the restricting nozzle throat 14 and the supersonic expansion nozzle section 15.
  • Abrasive particles P from a source identified by the arrow labeled, ABRASIVE PARTICLES are fed through radial passage 18 within the sidewall of the extended nozzle length 16, permitting the feed of the abrasive into the jet stream after expansion of the products of combustion to near atmospheric pressure and after a significant temperature drop within the jet stream.
  • the particles P enter a constant diameter bore 20 within the extended nozzle length 16 prior to exiting from the exit or outlet end 19 of the extended nozzle length.
  • the extended nozzle length 16 is shown as integral with the metal cylindrical body 10. Typically the extended nozzle length may be a replaceable nozzle tube of extremely hard metal.
  • a radial passage 17 is provided within the supersonic expansion nozzle section 15, upstream of its exit end 15a, at the junction between the supersonic expansion nozzle section 15 and the extended nozzle length 16. As indicated by the arrow labeled COOLANT, water or other coolant may be introduced under pressure through the small diameter radial passage 17 into the expanding jet stream J emanating from the combustion chamber 11.
  • the expanded jet velocity through the extended nozzle length 16 would be about 6,920 ft/sec, and the expanded jet J would be at a temperature of approximately 4,285° F.
  • Such apparatus operating under these parameters, and given a long enough acceleration duct (extended nozzle length 16), would speed abrasive particles P to velocities of 2,000 ft/sec, many of the smaller particles would have melted in standard nozzle length 16, leading to the plugging of tube 16 and causing the equipment to be rendered inoperable.
  • the jet temperature becomes 3,400° F. at 9,700 ft/sec at the exit 15a of the supersonic expansion nozzle section 15. From this (comprising operation of 1,200 psi against that at 125 psi), I have learned that lowering jet temperature to about 900° F. coupled with a 1,500 ft/sec increase in jet velocity permits a much longer acceleration passage by way of an increased extended nozzle length 16 beyond the exit 15a of the expansion nozzle section 15 for a given type abrasive, without the smallest particles thereof reaching fusion temperature.
  • the abrasive particles P have a particularly low melting point
  • the coolant is conveniently introduced upstream of and prior to particle P introduction as shown in FIG. 1.
  • the process of the present invention effects acceleration of the particles to extremely high velocity by the use of extended nozzle length 16 or accelerator ducts of up to 2 feet or more in length.
  • Each particle accomplishes manyfold that of the low temperature system.
  • oxygen costs are greater than compressed air costs, the savings in costs of the amount of abrasive required may result in a net savings using the method of the invention.
  • the method of this invention is particularly competitive where the surface cleaning involves extremely difficult-to-remove materials such as epoxy coatings, thick mill scale and the like.
  • the abrasive particles employed in the method of this invention are sand and steel shot.
  • the bore diameter 20 of the extended nozzle length 16 may range from 16 inches to 36 inches.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)

Abstract

A fuel and oxygen mixture is combusted within an internal burner combustion chamber at temperatures ranging from 250 psi to 1,000 psi. The products of combustion are directed through a restricting nozzle throat and a supersonic expansion nozzle section into an elongated duct formed by an extended nozzle length. Abrasive particles are introduced into the supersonic flow jet stream near the entrance to the elongated duct to accelerate the particles to extreme velocity, with the combustion pressure maintained sufficiently high to limit the jet stream temperature to that which is insufficient throughout the elongated duct to raise the particle temperatures to the plastic point of the particle material. The temperature of the supersonic gas flow through the elongated duct may be reduced by the introduction of a cooling flow into the jet stream beyond the flow-restricting nozzle throat. The cooling flow may be a flow of water or other liquid coolant or cool compressed air.

Description

FIELD OF THE INVENTION
This invention relates to sand blasting surfaces by impacting abrasive particles against such surface, and more particularly to the use of an internal burner in which an oxy-fuel mixture is combusted at very high pressure, with the abrasive particles for sandblasting introduced to the expanded gas products of combustion and accelerating such particle in an extended nozzle length downstream of the particle introduction point into expanded gases at near atmospheric pressure.
BACKGROUND OF THE INVENTION
In my U.S. Pat. No. 2,990,653, an application of rocket technology is employed to increase particle velocity in sandblast cleaning application by the use of internal burners powered by compressed air and a hydrocarbon fuel. The use of pure oxygen as the oxidant in a fuel and oxygen mixture fed to the combustion chamber of the internal burner has the severe advantage of melting some types of abrasives during particle transit through the gun, conventionally introduced upstream and of the internal burner combustion chamber. For this reason, pure oxygen could not be used as the oxidant source.
More recently, I have found that by using extremely high combustion pressures and introducing abrasive particles in the expanded gas, which has a temperature significantly below that of the products of combustion exiting from the combustion chamber, such allows the practical use of oxy-fuel internal burners for blast cleaning applications. This led to later work in similar air-fuel devices, in which the abrasive was added just upstream of the restricting nozzle passage, thereby eliminating the transit of the particles through the combustion chamber as exemplified by my U.S. Pat. No. 4,540,121.
SUMMARY OF THE INVENTION
The present invention is directed to a method of impacting abrasive particles against a surface to be treated, using an internal burner by introducing the abrasive particles into the supersonic jet stream after expansion of the product of combustion gases from the internal burner to nearly atmospheric pressure from very high pressures of the combustion chamber, and by causing the abrasive particles in their supersonic jet stream carrier gas to travel through an extended nozzle length, which nozzle length is long enough to accelerate the particles to much greater impact velocity than heretofore possible using either conventional compressed air sandblasting equipment or the air-fuel internal burner devices of my earlier patents, discussed above.
BRIEF DESCRIPTION OF THE DRAWING
The single figure is a cross-sectional view of an internal burner employing the method forming a preferred embodiment of the invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT
FIG. 1 is a cross-sectional view of an internal burner suitable for practicing the method of this invention. The internal burner indicated generally at 10' is comprised of a unitary metal, main body 10 of elongated cylindrical form which includes an axially positioned combustion chamber 11 of elongated cylindrical form, which is open at an upstream end 11a, to a small diameter axial bore or oxygen supply duct 12 receiving a source of oxygen under pressure as indicated by the labeled arrow. A fuel and oxygen mixture is effected by feeding fuel as indicated by the arrow labeled FUEL through a radial passage 13, which is at right angle to axial passage 12 and which intersects the same. The fuel and air mixture enters the combustion chamber and is combusted by a spark ignition device (not shown) or other conventional means. The downstream end 11b of the combustion chamber opens directly to a restricting nozzle throat 14 leading to a supersonic expansion nozzle section 15 of relatively short length. The internal burner 10' terminates in an integral, extended nozzle length 16 which is two, three or more times the combined length of the restricting nozzle throat 14 and the supersonic expansion nozzle section 15. Abrasive particles P from a source identified by the arrow labeled, ABRASIVE PARTICLES are fed through radial passage 18 within the sidewall of the extended nozzle length 16, permitting the feed of the abrasive into the jet stream after expansion of the products of combustion to near atmospheric pressure and after a significant temperature drop within the jet stream. The particles P enter a constant diameter bore 20 within the extended nozzle length 16 prior to exiting from the exit or outlet end 19 of the extended nozzle length. The extended nozzle length 16 is shown as integral with the metal cylindrical body 10. Typically the extended nozzle length may be a replaceable nozzle tube of extremely hard metal. A radial passage 17 is provided within the supersonic expansion nozzle section 15, upstream of its exit end 15a, at the junction between the supersonic expansion nozzle section 15 and the extended nozzle length 16. As indicated by the arrow labeled COOLANT, water or other coolant may be introduced under pressure through the small diameter radial passage 17 into the expanding jet stream J emanating from the combustion chamber 11.
If the oxy-fuel internal burner 10' of FIG. 1 were to be operated at conventional oxygen pressures, for instance, at 125 psi combustion pressure with a suitable supply of fuel through radial passage 13, the expanded jet velocity through the extended nozzle length 16 would be about 6,920 ft/sec, and the expanded jet J would be at a temperature of approximately 4,285° F. Although such apparatus operating under these parameters, and given a long enough acceleration duct (extended nozzle length 16), would speed abrasive particles P to velocities of 2,000 ft/sec, many of the smaller particles would have melted in standard nozzle length 16, leading to the plugging of tube 16 and causing the equipment to be rendered inoperable.
From a recent program, which I conducted, directed to the use of oxy-fuel internal burners operating at extremely high pressure, I have found that long nozzle ducts, said extended nozzle length 16, may be incorporated with the apparatus at the exit end of the supersonic expansion nozzle section 15 without fusing even the smallest abrasive particles. I have found that this beneficial result arises from the large expansion ratio of the hot products of combustion gases passing from the combustion chamber to atmospheric pressure. Calculated examples of the degree of jet J cooling obtained are given for 600 psi and 1,200 psi combustion chamber pressures as examples of the present invention, using a constant K=cp cv =1.1 and data from the publication "Gas Tables" by J. H. Keenan and J. Kaye, published by John Wiley & Sons, Inc. of New York, 1948.
As a first example, for 600 psi combustion pressure with a jet temperature of 3,700° F., a jet velocity of 8,580 ft/sec results.
For the second example where the combustion pressure within the combustion chamber is doubled to 1,200 psi, the jet temperature becomes 3,400° F. at 9,700 ft/sec at the exit 15a of the supersonic expansion nozzle section 15. From this (comprising operation of 1,200 psi against that at 125 psi), I have learned that lowering jet temperature to about 900° F. coupled with a 1,500 ft/sec increase in jet velocity permits a much longer acceleration passage by way of an increased extended nozzle length 16 beyond the exit 15a of the expansion nozzle section 15 for a given type abrasive, without the smallest particles thereof reaching fusion temperature.
I have determined that where the abrasive particles P have a particularly low melting point, it is preferable to introduce a small flow of coolant such as water, air or other cooling fluid into the expanded jet J to reduce the jet temperature sufficiently to prevent during particle transit over the extent of the nozzle bore 20 of the extended nozzle length 16 from the abrasive particle supply passage 18 to the exit end 19 of that nozzle length, without fusion of particles to the interior of the bore and the closing off of the nozzle bore. The coolant is conveniently introduced upstream of and prior to particle P introduction as shown in FIG. 1. The process of the present invention effects acceleration of the particles to extremely high velocity by the use of extended nozzle length 16 or accelerator ducts of up to 2 feet or more in length. For reactant flows of 1,800 SCFH of oxygen with six gallons of fuel oil per hour, the mass flow of the products of combustion (jet stream J) is about 190 pounds per hour. Assuming a jet speed of 8,000 ft/sec and an abrasive particle P flow of 100 pounds per hour, momentum considerations show that the particles P (under perfect conditions) reach a velocity of nearly a mile per second. Such extreme acceleration is probably not practical. It is reasonable to assume, however, an impact velocity against the workpiece W being cleaned, downstream of and in the path of the particles exiting the outlet of nozzle length 10, of 2,000 ft/sec; a value five times greater than that achieved by conventional cold compressed sandblasting.
The impact energy increase provided by combusting the oxidant (oxygen) at greatly elevated pressure is 52 =25:1. Each particle accomplishes manyfold that of the low temperature system. Where the oxygen costs are greater than compressed air costs, the savings in costs of the amount of abrasive required may result in a net savings using the method of the invention. The method of this invention is particularly competitive where the surface cleaning involves extremely difficult-to-remove materials such as epoxy coatings, thick mill scale and the like. Typically, the abrasive particles employed in the method of this invention are sand and steel shot. The bore diameter 20 of the extended nozzle length 16 may range from 16 inches to 36 inches.
While the invention has been described in terms of several examples, the invention is not limited thereto and changes may be made in the operating parameters without departing from the spirit of the invention, which is limited only to the extent of the claims appended hereto.

Claims (7)

What is claimed is:
1. A method of abrasive blasting a surface to be cleaned or treated comprising supplying an oxy-fuel mixture to an internal burner combustion chamber open at a downstream end to, in order, a restricting nozzle, a restricting nozzle throat, a supersonic expansion nozzle section, and an extended nozzle length forming an elongated duct by combusting said oxygen and fuel mixture within said combustion chamber, producing a flow of high-temperature products of combustion to supersonic velocity through said restricting nozzle throat and said supersonic expansion nozzle section, forming a jet stream and maintaining the supersonic flow through the elongated duct, introducing abrasive particles into the supersonic flow in the vicinity of said elongated duct to thereby accelerate the particles to extreme velocity, and maintaining the combustion pressure sufficiently high to limit the jet stream temperature passing through the elongated duct to a level which is insufficient to raise the temperature of the particle to the plastic point of the particles.
2. The method of claim 1, wherein the chamber pressure is maintained above 250 psi.
3. The method of claim 1, wherein the chamber pressure is maintained above 500 psi.
4. The method of claim 1, wherein the chamber pressure is maintained above 1,000 psi.
5. The method of claim 1, further comprising the step of reducing the temperature of the supersonic gas flow through said elongated duct by cooling the jet stream beyond the flow-restricting nozzle.
6. The method as claimed in claim 5, wherein said cooling step comprises injecting a flow of water into the jet stream upstream of the extended nozzle length.
7. The method of claim 5, wherein said cooling step comprises injecting a flow of compressed air into the jet steam upstream of the extended nozzle length.
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US5484325A (en) * 1993-10-07 1996-01-16 Church & Dwight Co., Inc. Blast nozzle containing water atomizer for dust control
US5795626A (en) * 1995-04-28 1998-08-18 Innovative Technology Inc. Coating or ablation applicator with a debris recovery attachment
WO1998042380A2 (en) * 1997-03-21 1998-10-01 The Johns Hopkins University Lubricated nozzle for fluid jet cutting
US5957760A (en) * 1996-03-14 1999-09-28 Kreativ, Inc Supersonic converging-diverging nozzle for use on biological organisms
US6659844B2 (en) * 2001-05-29 2003-12-09 General Electric Company Pliant coating stripping
WO2004038064A1 (en) * 2002-10-24 2004-05-06 Oao 'investitsionnaya Kompaniya Sotsialnoy Zaschity I Razvitiya Malochislennykh Narodov Severa 'titul' Method for surface processing, method for surface preparation for subsequent coating and devices for carrying out said methods
US20040215135A1 (en) * 2001-01-11 2004-10-28 Sheldrake Colin David Needleless syringe
US6948306B1 (en) * 2002-12-24 2005-09-27 The United States Of America As Represented By The Secretary Of The Navy Apparatus and method of using supersonic combustion heater for hypersonic materials and propulsion testing
US20060275554A1 (en) * 2004-08-23 2006-12-07 Zhibo Zhao High performance kinetic spray nozzle
US7314527B1 (en) * 2001-12-10 2008-01-01 Lsi Logic Corporation Reactor system
WO2008005460A2 (en) * 2006-07-06 2008-01-10 Praxair Technology, Inc Controlling jet momentum in process streams
US20090227185A1 (en) * 2008-03-10 2009-09-10 David Archibold Summers Method and apparatus for jet-assisted drilling or cutting
US20090286190A1 (en) * 2008-05-19 2009-11-19 Browning James A Method and apparatus for combusting fuel employing vortex stabilization
US20100111830A1 (en) * 2008-10-31 2010-05-06 Searete Llc Compositions and methods for surface abrasion with frozen particles
US20100111834A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for therapeutic delivery with frozen particles
US20100114348A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The States Of Delaware Frozen compositions and methods for piercing a substrate
US20100111833A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for surface abrasion with frozen particles
US20100114547A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for biological remodeling wih frozen particle compositions
US20100111831A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for surface abrasion with frozen particles
US20100111843A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for therapeutic delivery with frozen particles
US20100111836A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for therapeutic delivery with frozen particles
US20100111832A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for surface abrasion with frozen particles
US20100111841A1 (en) * 2008-10-31 2010-05-06 Searete Llc Compositions and methods for surface abrasion with frozen particles
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US20100111857A1 (en) * 2008-10-31 2010-05-06 Boyden Edward S Compositions and methods for surface abrasion with frozen particles
US20100111846A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for delivery of frozen particle adhesives
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US20100113615A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for delivery of frozen particle adhesives
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US20100114496A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for surface abrasion with frozen particles
US20100111938A1 (en) * 2008-10-31 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Compositions and methods for biological remodeling with frozen particle compositions
US20100121262A1 (en) * 2007-05-04 2010-05-13 Lee's Pharmaceutical (Hk), Ltd. Particle cassettes and processes therefor
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US20100281873A1 (en) * 2002-12-24 2010-11-11 United States Of America As Represented By The Secretary Of The Navy Variable Supersonic Mach Number Air Heater Utilizing Supersonic Combustion
US8409376B2 (en) 2008-10-31 2013-04-02 The Invention Science Fund I, Llc Compositions and methods for surface abrasion with frozen particles
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US8731841B2 (en) 2008-10-31 2014-05-20 The Invention Science Fund I, Llc Compositions and methods for therapeutic delivery with frozen particles
US8731840B2 (en) 2008-10-31 2014-05-20 The Invention Science Fund I, Llc Compositions and methods for therapeutic delivery with frozen particles
US8788211B2 (en) 2008-10-31 2014-07-22 The Invention Science Fund I, Llc Method and system for comparing tissue ablation or abrasion data to data related to administration of a frozen particle composition
US9060926B2 (en) 2008-10-31 2015-06-23 The Invention Science Fund I, Llc Compositions and methods for therapeutic delivery with frozen particles
US9072688B2 (en) 2008-10-31 2015-07-07 The Invention Science Fund I, Llc Compositions and methods for therapeutic delivery with frozen particles
US20190134780A1 (en) * 2017-05-26 2019-05-09 Thomas Francis Hursen Abrasive media blasting method and apparatus
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US2990653A (en) * 1958-04-21 1961-07-04 G H Temant Company Method and apparatus for impacting a stream at high velocity against a surface to be treated
US3854997A (en) * 1970-12-14 1974-12-17 Peck Co C Jet flame cleaning
SU423619A2 (en) * 1971-11-01 1974-04-15 Всесоюзный проектно технологический институт GASAL EQUIPMENT HEAD OF JETS

Cited By (111)

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US5484325A (en) * 1993-10-07 1996-01-16 Church & Dwight Co., Inc. Blast nozzle containing water atomizer for dust control
US5795626A (en) * 1995-04-28 1998-08-18 Innovative Technology Inc. Coating or ablation applicator with a debris recovery attachment
US5957760A (en) * 1996-03-14 1999-09-28 Kreativ, Inc Supersonic converging-diverging nozzle for use on biological organisms
US6273789B1 (en) 1996-03-14 2001-08-14 Lasalle Richard Todd Method of use for supersonic converging-diverging air abrasion nozzle for use on biological organisms
WO1998042380A2 (en) * 1997-03-21 1998-10-01 The Johns Hopkins University Lubricated nozzle for fluid jet cutting
WO1998042380A3 (en) * 1997-03-21 1998-11-05 Univ Johns Hopkins Lubricated nozzle for fluid jet cutting
US20040215135A1 (en) * 2001-01-11 2004-10-28 Sheldrake Colin David Needleless syringe
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